An analytical model for predicting the aeroelastic behavior of composite rotor blades with straight and swept tips is presented. The blade is modeled by beam type finite elements along the elastic axis. A single finite element is used to model the swept tip. The nonlinear equations of motion for the finite element model are derived using Hamilton's principle and based on a moderate deflection theory and accounts for: arbitray cross-sectional shape, pretwist, generally anisotropic material behavior, transverse shears nd out-of-plane warping. Numerical results illustrating the effects of tip sweep, anhedral and composite ply orientation on blade aeroelastic behavior are presented. Tip sweep can induce aeroelastic instability by lap-twist coupling. Tip anhedral causes lag-torsion and flap-axial couplings, however its effect on blade stability is less pronounced than the effect due to sweep. Composite ply orientation has a substantial effect on blade stability.
A new aeroelastic model for composite rotor blades with straight and swept tips
Ein neues aeroelastisches Modell für Drehflügelblätter aus Verbundwerkstoff mit geraden und gebogenen Spitzen
AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 33 ; 3 , Apr ; 1371-1390
1992
20 Seiten, 16 Bilder, 2 Tabellen, 34 Quellen
Conference paper
English